CN201780198U - Wind-tunnel high attack angle dynamic testing device based on hybrid mechanism - Google Patents
Wind-tunnel high attack angle dynamic testing device based on hybrid mechanism Download PDFInfo
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- CN201780198U CN201780198U CN2010205119048U CN201020511904U CN201780198U CN 201780198 U CN201780198 U CN 201780198U CN 2010205119048 U CN2010205119048 U CN 2010205119048U CN 201020511904 U CN201020511904 U CN 201020511904U CN 201780198 U CN201780198 U CN 201780198U
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Abstract
A wind-tunnel high attack angle dynamic testing device based on a hybrid mechanism belongs to an aircraft testing device, and comprises a base (1), three kinematic chains (3), a moving platform (9), a bent blade (8), a first driving rotating joint (5), an end actuator (6), and a second driving rotating joint (7). One end of the bent blade (8) is connected with the moving platform (9) through the first driving rotating joint (5), the end actuator (6) is connected with the other end of the bent blade through the second driving rotating joint (7), a rotating axis of the first driving rotating joint is perpendicular to the moving platform, and a rotating axis of the second driving rotating joint is parallel to the moving platform and is coincident with a body axis of the end actuator (6). By utilizing a three-degrees-of-freedom planar parallel mechanism and a serial two-degrees-of-freedom rotating device, the wind-tunnel high attack angle dynamic testing device based on a hybrid mechanism can complete three degrees of freedom rotation around a fixed point on an aircraft and is large in moving space, simple in structure, low in cost and easy to operate.
Description
Technical field
The utility model belongs to a kind of air vehicle experimental device, and particularly certain point of fixity is realized the high-angle-of attack dynamic experimental device of wind tunnel that Three Degree Of Freedom rotates on aircraft.
Background technology
A new generation's aircraft requires to have higher agility and maneuverability.For the non-permanent aerodynamic force in the exploratory flight device mobile process, need innovation to some extent on wind-tunnel technique.At present, carry out many researchs in big angle of attack nonsteady aerodynamics field both at home and abroad, particularly aspect wind-tunnel technique, built up the large amplitude dynamic experimental device of many simulation fighter planes maneuvering flight.(see: http://www.nrc-cnrc.gc.ca/eng/programs/iar/non-linear.html) as in 3 meters wind-tunnel of Canadian aerospace research institute, disclosing a kind of dynamic experimental device; Figure is the disclosed cover dynamic experimental device of U.S. Stanford university; Russia center air fluid dynamic research center also discloses similar dynamic experimental device.These devices can only be realized the motion control to the model attitude single-degree-of-freedom.The cover that Virginia university discloses can realize that the dynamic experimental device of two-freedom motion (sees: http://www.aoe.vt.edu/research/facilities/dyppir); Nanjing Aero-Space University has developed a cover voluntarily can realize that the dynamic experimental device of pitching-lift-over two-freedom motion (sees document " pitching-lift-over coupling two-freedom large amplitude unsteady aerodynamic test technology ", Nanjing Aero-Space University's journal, 1999,31 (2)).These devices can be realized the two-freedom motion control to model attitude.Other also have the dynamic experimental device of the U.S.'s 3 meters wind-tunnel in langley center, and also there is similar large amplitude dynamic experimental device in unit such as domestic 627,29 bases.
From these experimental facilities, most of dynamic experimental devices can only be realized the motion of one degree of freedom, minority has realized the motion of two degree of freedom, and these motions can only be finished the motion of simple simple harmonic oscillation, the compound movement of fighter plane in the time of can not the maneuvering flight of real simulation actual fault speed.
From the prior art, the experimental facilities the most approaching with the utility model has the MPM experimental provision of German DLR (to see document " Ground-based simulation of complex maneuvers of a delta-wing aircraft ", Journal of Aircraft, 2008,45 (1)).What this device adopted is the six-freedom parallel driving mechanism, can realize the Three Degree Of Freedom of model attitude is rotated control, but the space of this telecontrol equipment is smaller, and motion drives more complicated.
Before the utility model, finish the rotation that certain point of fixity can be realized on aircraft and mostly be single-degree-of-freedom or two degree of freedom most, and these devices adopted mostly be series connection, open-chain structure, action response is slow; Model attitude control system space based on parallel institution is smaller, and motion drives complicated.The utility model will overcome these shortcomings, and it is big to have a space, characteristics such as mechanism freedom is few, and is simple in structure.
Summary of the invention
Order of the present utility model is to provide a kind of work space big and response speed good, and controls the easy high-angle-of attack dynamic experimental device of wind tunnel based on hybrid mechanism.
A kind of high-angle-of attack dynamic experimental device of wind tunnel based on hybrid mechanism is characterized in that:
This experimental provision comprises pedestal, three kinematic chains, moving platform; Above-mentioned every kinematic chain is formed by the active moving sets in the middle of being positioned at, the second driven revolute pair that is coupled to the first driven revolute pair of active moving sets lower end and is coupled to active moving sets upper end; The first driven revolute pair and pedestal link, and the second driven revolute pair and moving platform link; Pedestal, moving platform and three kinematic chains that connect both have constituted one jointly to have two and moves and the plane parallel mechanism of a rotational freedom;
This experimental provision also comprises tulwar, the first active rotation joint, end effector, the second active rotation joint; One end of tulwar is installed on the moving platform by the first active rotation joint, and end effector is installed on the other end of tulwar by the second active rotation joint; The turning axle of above-mentioned first cradle head is perpendicular to moving platform, and the rotating shaft parallel of second cradle head is in moving platform, and the axon of end effector self overlaps with the turning axle of second cradle head.
Characteristics of the present utility model are: utilize the two-freedom wheelwork of three-DOF planar parallel mechanism and series connection, the space three-freedom of finishing certain point of fixity on aircraft rotates.Space is big, simple in structure, cost is low, easy enforcement.
Description of drawings
Fig. 1 is the schematic diagram that the utility model certain point of fixity on aircraft is realized the Three Degree Of Freedom wheelwork.
Number in the figure title: 1. pedestal, 2. the first driven revolute pair, 3. active moving sets, the 4. second driven revolute pair, the 5. first active cradle head, 6. end effector, 7. the second active cradle head, 8. tulwar, 9. moving platform, MN. the axis of rotation of the first active cradle head, the axis of rotation of the MP. second active cradle head.
Embodiment
As shown in Figure 1, pedestal 1 is connected by three RPR kinematic chains are parallel with moving platform 9, these three kinematic chains are in same plane X OY or be in the Different Plane that is parallel to XOY plane, with pedestal 1 and moving platform 9 common constitute have two planar three freedom parallel institutions that move rotations.Article three, kinematic chain is the kinematic chain of RPR form, and moving sets P is joint initiatively, can adopt hydraulic cylinder, electrical pushing cylinder when specifically using or is implemented to drive by motor-driven screw pair etc., and two revolute pair R are driven pair.Article three, the coordinated movement of various economic factors of RPR kinematic chain can make moving platform finish two mobile and rotation works in XOY plane.
Moving platform 9 is connected by the first active cradle head 5 with tulwar 8, and its axis of rotation MN is perpendicular to moving platform 9, and in XOY plane.The first active cradle head 5 can use motor or rotating hydraulic cylinder to drive during enforcement.The other end of tulwar 8 is connected with end effector 6 by the second active cradle head 7, and the axis of rotation MP of the second active cradle head 7 overlaps with the axon of end effector 6, is vertically intersected on the M point with the axis of rotation MN of the first active cradle head 5.The second active cradle head can use motor or rotating hydraulic cylinder to drive during enforcement.This device can be finished three rotation works that M is ordered on end effector 6.Because end effector 6 has certain length, therefore, will make moving platform 9 be created in the displacement on the both direction in the XOY plane during rotation.
Claims (1)
1. high-angle-of attack dynamic experimental device of wind tunnel based on hybrid mechanism is characterized in that:
This experimental provision comprises pedestal (1), three kinematic chains, moving platform (9); Above-mentioned every kinematic chain by the active moving sets (3) in the middle of being positioned at, be coupled to the first driven revolute pair (2) of active moving sets lower end and be coupled to the second driven revolute pair (4) composition of active moving sets upper end; The first driven revolute pair (2) links with pedestal (1), and the second driven revolute pair (4) links with moving platform (9); Pedestal (1), moving platform (9) and three kinematic chains that connect both have constituted one jointly to have two and moves and the plane parallel mechanism of a rotational freedom;
This experimental provision also comprises tulwar (8), the first active rotation joint (5), end effector (6), the second active rotation joint (7); One end of tulwar (8) is installed on the moving platform (9) by the first active rotation joint (5), and end effector (6) is installed on the other end of tulwar by the second active rotation joint (7); The turning axle of above-mentioned first cradle head is perpendicular to moving platform, and the rotating shaft parallel of second cradle head is in moving platform, and the axon of end effector (6) self overlaps with the turning axle of second cradle head.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010205119048U CN201780198U (en) | 2010-08-30 | 2010-08-30 | Wind-tunnel high attack angle dynamic testing device based on hybrid mechanism |
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| CN2010205119048U CN201780198U (en) | 2010-08-30 | 2010-08-30 | Wind-tunnel high attack angle dynamic testing device based on hybrid mechanism |
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| CN201780198U true CN201780198U (en) | 2011-03-30 |
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| CN2010205119048U Expired - Lifetime CN201780198U (en) | 2010-08-30 | 2010-08-30 | Wind-tunnel high attack angle dynamic testing device based on hybrid mechanism |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101929915A (en) * | 2010-08-30 | 2010-12-29 | 南京航空航天大学 | Hybrid mechanism-based high-angle-of attack dynamic experimental device of wind tunnel |
| CN102901613A (en) * | 2012-09-29 | 2013-01-30 | 中国航天空气动力技术研究院 | Method for determining pressure center of reentry vehicle |
| CN103495973A (en) * | 2013-09-28 | 2014-01-08 | 孙志超 | Planar three-freedom-degree parallel mechanism driven by three linear drivers and application thereof |
| CN105571811A (en) * | 2015-12-22 | 2016-05-11 | 中国航天空气动力技术研究院 | Method of measuring aircraft actual attack angle value in wind tunnel experiment |
| CN107063619A (en) * | 2016-12-14 | 2017-08-18 | 中国航天空气动力技术研究院 | A kind of low speed wind tunnel thrust vector test at high attack angle device |
| CN107290123A (en) * | 2017-06-07 | 2017-10-24 | 中国航天空气动力技术研究院 | The big angle of attack device of multiple degrees of freedom wind-tunnel |
-
2010
- 2010-08-30 CN CN2010205119048U patent/CN201780198U/en not_active Expired - Lifetime
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101929915A (en) * | 2010-08-30 | 2010-12-29 | 南京航空航天大学 | Hybrid mechanism-based high-angle-of attack dynamic experimental device of wind tunnel |
| CN101929915B (en) * | 2010-08-30 | 2011-11-30 | 南京航空航天大学 | Hybrid mechanism-based large attack angle dynamic experimental device of wind tunnel |
| CN102901613A (en) * | 2012-09-29 | 2013-01-30 | 中国航天空气动力技术研究院 | Method for determining pressure center of reentry vehicle |
| CN102901613B (en) * | 2012-09-29 | 2014-11-26 | 中国航天空气动力技术研究院 | Method for determining pressure center of reentry vehicle |
| CN103495973A (en) * | 2013-09-28 | 2014-01-08 | 孙志超 | Planar three-freedom-degree parallel mechanism driven by three linear drivers and application thereof |
| CN103495973B (en) * | 2013-09-28 | 2015-06-17 | 新乡学院 | Planar three-freedom-degree parallel mechanism driven by three linear drivers and application thereof |
| CN105571811A (en) * | 2015-12-22 | 2016-05-11 | 中国航天空气动力技术研究院 | Method of measuring aircraft actual attack angle value in wind tunnel experiment |
| CN105571811B (en) * | 2015-12-22 | 2018-02-06 | 中国航天空气动力技术研究院 | The method for measuring aerocraft real angle of attack value in wind tunnel experiment |
| CN107063619A (en) * | 2016-12-14 | 2017-08-18 | 中国航天空气动力技术研究院 | A kind of low speed wind tunnel thrust vector test at high attack angle device |
| CN107063619B (en) * | 2016-12-14 | 2019-07-12 | 中国航天空气动力技术研究院 | A kind of low speed wind tunnel thrust vector test at high attack angle device |
| CN107290123A (en) * | 2017-06-07 | 2017-10-24 | 中国航天空气动力技术研究院 | The big angle of attack device of multiple degrees of freedom wind-tunnel |
| CN107290123B (en) * | 2017-06-07 | 2019-05-24 | 中国航天空气动力技术研究院 | The big angle of attack device of multiple degrees of freedom wind-tunnel |
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| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20110330 Effective date of abandoning: 20111130 |